HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/8 AIRFOIL (hq308-il) Reynolds number: 100,000 Max Cl/Cd: 62.54 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq308-il-100000.txt Download as CSV file: xf-hq308-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3856 0.09511 0.09046 -0.0340 1.0000 0.0672
-7.750 -0.3962 0.09334 0.08881 -0.0347 1.0000 0.0676
-7.500 -0.4062 0.09113 0.08672 -0.0386 1.0000 0.0679
-7.250 -0.4120 0.08828 0.08390 -0.0426 1.0000 0.0681
-7.000 -0.3958 0.08367 0.07931 -0.0306 1.0000 0.0733
-6.750 -0.3999 0.08116 0.07687 -0.0305 1.0000 0.0756
-6.500 -0.4051 0.07844 0.07422 -0.0317 1.0000 0.0778
-6.250 -0.4097 0.07534 0.07111 -0.0370 1.0000 0.0805
-6.000 -0.4113 0.07262 0.06817 -0.0445 1.0000 0.0820
-5.750 -0.4086 0.06816 0.06395 -0.0379 1.0000 0.0843
-5.500 -0.4044 0.06551 0.06134 -0.0362 1.0000 0.0878
-5.250 -0.3902 0.06192 0.05728 -0.0447 1.0000 0.0959
-5.000 -0.3860 0.05804 0.05367 -0.0410 1.0000 0.0986
-4.750 -0.3674 0.05498 0.05020 -0.0455 1.0000 0.1098
-4.500 -0.3597 0.05157 0.04701 -0.0429 1.0000 0.1142
-4.250 -0.3423 0.04826 0.04354 -0.0447 1.0000 0.1267
-4.000 -0.3246 0.04531 0.04048 -0.0456 1.0000 0.1412
-3.750 -0.3041 0.04262 0.03757 -0.0473 1.0000 0.1657
-3.500 -0.2872 0.04013 0.03511 -0.0469 1.0000 0.1857
-3.000 -0.1886 0.03134 0.02389 -0.0520 1.0000 0.0685
-2.750 -0.1570 0.02758 0.01963 -0.0523 1.0000 0.0557
-2.500 -0.1302 0.02558 0.01735 -0.0521 1.0000 0.0535
-2.250 -0.1036 0.02386 0.01522 -0.0520 1.0000 0.0564
-2.000 -0.0782 0.02238 0.01363 -0.0517 1.0000 0.0595
-1.750 -0.0527 0.02118 0.01227 -0.0511 1.0000 0.0620
-1.500 -0.0269 0.02028 0.01122 -0.0505 0.9998 0.0678
-1.250 0.0124 0.01893 0.01013 -0.0528 0.9955 0.1022
-1.000 0.0335 0.01572 0.00992 -0.0498 0.9938 0.8439
-0.750 0.0786 0.01574 0.00958 -0.0535 0.9849 1.0000
-0.500 0.1201 0.01622 0.00969 -0.0569 0.9771 1.0000
-0.250 0.1646 0.01672 0.00990 -0.0608 0.9697 1.0000
0.000 0.2023 0.01708 0.01004 -0.0634 0.9602 1.0000
0.250 0.2436 0.01748 0.01023 -0.0665 0.9517 1.0000
0.500 0.2861 0.01783 0.01044 -0.0698 0.9431 1.0000
0.750 0.3217 0.01812 0.01063 -0.0718 0.9329 1.0000
1.000 0.3607 0.01840 0.01082 -0.0742 0.9236 1.0000
1.250 0.4083 0.01855 0.01092 -0.0781 0.9152 1.0000
1.500 0.4469 0.01862 0.01097 -0.0801 0.9033 1.0000
1.750 0.4868 0.01862 0.01097 -0.0822 0.8915 1.0000
2.000 0.5274 0.01857 0.01097 -0.0844 0.8804 1.0000
2.250 0.5726 0.01838 0.01083 -0.0872 0.8707 1.0000
2.500 0.6190 0.01799 0.01051 -0.0898 0.8615 1.0000
2.750 0.6568 0.01761 0.01021 -0.0907 0.8484 1.0000
3.000 0.6937 0.01714 0.00988 -0.0911 0.8347 1.0000
3.250 0.7284 0.01669 0.00951 -0.0911 0.8205 1.0000
3.500 0.7555 0.01647 0.00939 -0.0901 0.8024 1.0000
3.750 0.7859 0.01610 0.00912 -0.0893 0.7848 1.0000
4.000 0.8176 0.01563 0.00881 -0.0886 0.7666 1.0000
4.250 0.8436 0.01538 0.00866 -0.0871 0.7421 1.0000
4.500 0.8702 0.01511 0.00846 -0.0856 0.7144 1.0000
4.750 0.8951 0.01497 0.00837 -0.0839 0.6801 1.0000
5.000 0.9193 0.01492 0.00833 -0.0821 0.6376 1.0000
5.250 0.9418 0.01506 0.00845 -0.0802 0.5842 1.0000
5.500 0.9620 0.01549 0.00864 -0.0780 0.5195 1.0000
5.750 0.9798 0.01626 0.00906 -0.0758 0.4500 1.0000
6.000 0.9965 0.01723 0.00968 -0.0737 0.3867 1.0000
6.250 1.0135 0.01823 0.01042 -0.0719 0.3315 1.0000
6.500 1.0307 0.01925 0.01127 -0.0702 0.2830 1.0000
6.750 1.0473 0.02039 0.01223 -0.0685 0.2388 1.0000
7.000 1.0620 0.02167 0.01332 -0.0666 0.1868 1.0000
7.250 1.0744 0.02327 0.01468 -0.0646 0.1330 1.0000
7.500 1.0884 0.02479 0.01597 -0.0629 0.0883 1.0000
7.750 1.0988 0.02706 0.01806 -0.0604 0.0578 1.0000
8.000 1.1096 0.03035 0.02122 -0.0578 0.0435 1.0000
8.250 1.1311 0.03298 0.02408 -0.0562 0.0374 1.0000
8.500 1.1528 0.03679 0.02791 -0.0556 0.0331 1.0000
8.750 1.1709 0.03945 0.03102 -0.0540 0.0306 1.0000
9.000 1.1862 0.04234 0.03435 -0.0522 0.0285 1.0000
9.250 1.1974 0.04608 0.03857 -0.0501 0.0279 1.0000
9.500 1.2025 0.05012 0.04312 -0.0476 0.0281 1.0000
9.750 1.2013 0.05430 0.04779 -0.0448 0.0284 1.0000
10.000 1.1950 0.05848 0.05238 -0.0419 0.0288 1.0000
10.250 1.1826 0.06235 0.05659 -0.0387 0.0292 1.0000
10.500 1.1663 0.06611 0.06062 -0.0359 0.0296 1.0000
10.750 1.1482 0.07012 0.06488 -0.0340 0.0299 1.0000
11.000 1.1289 0.07456 0.06953 -0.0333 0.0302 1.0000
11.250 1.1086 0.07951 0.07468 -0.0338 0.0304 1.0000
11.500 1.0881 0.08508 0.08042 -0.0356 0.0307 1.0000
11.750 1.0669 0.09150 0.08700 -0.0389 0.0309 1.0000
12.000 1.0460 0.09883 0.09445 -0.0434 0.0312 1.0000
12.250 1.0266 0.10705 0.10275 -0.0490 0.0316 1.0000
12.500 1.0096 0.11589 0.11165 -0.0547 0.0320 1.0000
12.750 0.8345 0.13121 0.12746 -0.0597 0.0423 1.0000
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Polar data table (+)
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